EP2784270A2 - Système d'actionnement et carburant pour moteur de turbine à gaz - Google Patents

Système d'actionnement et carburant pour moteur de turbine à gaz Download PDF

Info

Publication number
EP2784270A2
EP2784270A2 EP14158333.6A EP14158333A EP2784270A2 EP 2784270 A2 EP2784270 A2 EP 2784270A2 EP 14158333 A EP14158333 A EP 14158333A EP 2784270 A2 EP2784270 A2 EP 2784270A2
Authority
EP
European Patent Office
Prior art keywords
fuel
pump
motive
main
actuator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14158333.6A
Other languages
German (de)
English (en)
Other versions
EP2784270A3 (fr
EP2784270B1 (fr
Inventor
Leo J. Veilleux
Gary M. Mcbrien
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Publication of EP2784270A2 publication Critical patent/EP2784270A2/fr
Publication of EP2784270A3 publication Critical patent/EP2784270A3/fr
Application granted granted Critical
Publication of EP2784270B1 publication Critical patent/EP2784270B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/236—Fuel delivery systems comprising two or more pumps

Definitions

  • the present disclosure relates generally to fuel systems for gas turbine engines.
  • the present disclosure relates to fuel systems utilizing fuel flow to operate engine actuation systems.
  • a main fuel pump is used to deliver fuel to a fuel metering valve that provides fuel directly to fuel injectors in the combustion section of the engine. Additionally, some of the fuel flow from the main fuel pump is circulated through actuators that operate other engine or aircraft systems. Such a system is described in U.S. Pat. No. 4,487,016 , which is assigned to United Technologies Corporation.
  • fuel flow is metered using a servo valve-controlled torque motor that provides fuel based on engine requirements for different speeds.
  • servo valve-controlled valves are used to regulate airflow to active clearance control systems and variable vane systems based on fuel flow. The servo valves utilize fuel flow from the main fuel pump to provide actuation.
  • the main fuel pump needs to be sized at a minimum to provide flow to the servo valves and to the injectors at idle engine speed, and at a maximum to provide flow to the servo valves and to the injectors under transient engine conditions, such as during take-off.
  • the main fuel pump must have a large capacity to accommodate the entire engine operating envelope and to provide fuel to other various aircraft systems.
  • the large pump capacity produces inefficiencies in the engine, such as consuming excess system horsepower and generating waste heat.
  • the servo valve-controlled actuators need to be sized to withstand the elevated pressures generated during transient conditions and the associated fatigue stress with such a wide operating envelope. There is, therefore, a need for a more efficient fuel and actuation system for gas turbine engines.
  • a fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump.
  • the boost pump receives fuel from a storage unit.
  • the main fuel pump receives fuel from the boost pump and delivers fuel to a distribution system.
  • the motive fuel pump receives fuel from the boost pump, routes fuel through the storage unit, and delivers fuel to an actuator.
  • the present disclosure is directed to a method for delivering fuel in an aircraft.
  • the method comprises pumping fuel from a fuel tank to a distribution system using a main pump, and pumping fuel from a fuel tank to an actuator using a motive pump.
  • the method also comprises routing fuel from the actuator to the main pump.
  • the sole figure shows a fuel and actuation system utilizing a main fuel pump and a motive fuel pump to deliver fuel flows to a combustion system and to actuators.
  • the sole figure shows fuel and actuation system 10 utilizing main fuel pump 12 and motive fuel pump 14 to deliver fuel flows to distribution system 16 and actuators 18A and 18B.
  • the present disclosure is described with reference to a fuel system for gas turbine engine 19 that utilizes fuel flow to operate aircraft system actuators.
  • the fuel and actuation system described herein may be used with other aircraft or non-aircraft systems.
  • Boost pump 22 provides fuel flow to main fuel pump 12 and motive pump 14.
  • Heat exchanger 24 and filter 26 are fluidly positioned between boost pump 22 and main fuel pump 12 in series connection.
  • Main fuel pump 12 delivers fuel to distribution system 16, which comprises manifold 28, valves 30A and 30B, and injectors 32A, 32B, 34A and 34B.
  • Main fuel pump 12, through distribution system 16 provides fuel to combustor 35 in gas turbine engine 19 where a combustion process that consumes fuel occurs.
  • Motive pump 14 provides fuel to ejector 36 to circulate or distribute fuel within fuel tank 20, and also provides fuel to actuators 18A and 18B to control various operations related to gas turbine engine 19.
  • Main fuel pump 12 and motive pump 14 are mechanically operated based on shaft speed within gas turbine engine 19. Thus, at higher shaft speeds, pumps 12 and 14 provide higher volumetric flow rates of fuel.
  • Boost pump 22 draws in fuel from fuel tank 20 through shut-off valve 37 and pumps the fuel to heat exchanger 24.
  • Heat exchanger 24 is fluidly coupled to fluid flow 38 of another liquid, such as oil or another lubricant, that is at a different temperature than the fuel from boost pump 22.
  • heat exchanger 24 comprises a fuel/oil cooler that transfers heat from oil used to lubricate various aircraft systems, such as bearings, to the fuel.
  • fuel is routed to filter 26.
  • Main fuel pump 12 provides fuel to distribution system 16, which includes many small orifices, such as those in injectors 32A - 34B.
  • Filter 26 removes contaminants from the fuel before being routed to main fuel pump 12 to avoid formation of blockages within main fuel pump 12 and distribution system 16.
  • filter 26 comprises a screen with a bypass valve.
  • Main fuel pump 12 provides fuel directly to manifold 28, which distributes fuel to a plurality of valves.
  • Fuel valves 30A and 30B distribute fuel to fuel injectors 32A - 34B as needed by gas turbine engine 19.
  • injectors 32A - 34B provide fuel to combustor 35 within gas turbine engine 19 where combustion process is executed using the fuel.
  • the combustion process operates gas turbine engine 19 to provide shaft power or thrust that drives an aircraft.
  • valves 30A and 30B are electronically operated metering valves controlled by a control system for gas turbine engine 19.
  • Injectors 32A - 34B may comprise primary and secondary fuel injectors that deliver fuel to different parts of combustor 35 at different times during the combustion process.
  • Fuel flow from main fuel pump 12 also includes pressure relief valve 40 and pressure regulating valve 42.
  • Pressure relief valve 40 allows fuel from the high pressure side of main fuel pump 12 to be returned to the low pressure side of main fuel pump 12, such as at the inlet of filter 26.
  • Pressure relief valve 40 typically automatically opens when pressure at the high pressure side of main fuel pump 12 becomes higher than a system maximum to prevent system over-pressurization.
  • Pressure regulating valve 42 returns fuel unneeded by distribution system 16 to the low pressure side of main fuel pump 12, such as at the inlet of filter 26.
  • main fuel pump 12 operates to provide a steady flow of fuel to manifold 28 at different operating speeds of gas turbine engine 19.
  • main fuel pump 12 can provide more fuel than is needed by combustor 35.
  • pressure regulating valve 42 returns unconsumed fuel back through fuel system 10.
  • pressure regulating valve 42 comprises an electronically operated valve, such as a direct drive valve, that is controlled by a control system for gas turbine engine 19.
  • pressure regulating valve 42 comprises a servo valve that operates based on fuel flow as do actuators 18A and 18B, which will be described in detail below.
  • boost pump 22 In addition to providing burn flow to distribution system 16 and combustor 35 through main fuel pump 12, boost pump 22 also pumps fuel from fuel tank 20 to motive pump 14.
  • Motive pump 14 provides fuel flow to ejector 36, which is used to distribute fuel within fuel tank 20.
  • ejector 36 transfers fuel from different partitions 20A, 20B within fuel tank 20, such as those that are located in different wings of the aircraft.
  • Such distribution and circulation of fuel within fuel tank 20 ensures that boost pump 22 will be adequately primed with fuel at different fuel level and at different aircraft orientations.
  • Fuel from within fuel tank 20 is provided to boost pump 22 through shut-off valve 37.
  • Valve 37 can be closed to fluidly isolate fuel tank 20 from boost pump 22 such as for maintenance operations and the like.
  • Motive pump 14 additionally directly provides fuel flow to one or more actuators.
  • motive pump 14 may also provide fuel flow to a servo valve for various embodiments of pressure regulating valve 42.
  • fuel and actuation system 10 includes two actuators 18A and 18B.
  • actuators 18A and 18B comprise servo valves that are operated by fuel flow from motive pump 14.
  • actuators 18A and 18B include butterfly valves that are actuated based on the volume of fuel flow provided by motive pump 14.
  • Actuators 18A and 18B regulate airflows 44A and 44B, respectively, to other parts of gas turbine engine 19.
  • actuator 18A may actuate an active clearance control air valve that provides airflow 44A to change the clearance gap in turbine section 46 of gas turbine engine 19.
  • actuator 18B may actuate a bleed valve that controls bleed airflow 44B from compressor section 48 of gas turbine engine 19 for various uses, such as clearance control systems.
  • actuators 18A and 18B may comprise a linear actuator that changes the position of a variable vane.
  • heat exchangers may be connected into system 10 upstream of actuators 18A and 18B to warm the fuel flow before interacting with airflows 44A and 44B. After providing actuation power to actuators 18A and 18B, fuel is returned to fuel and actuation system 10, such as at the inlet of main fuel pump 12.
  • Motive pump 14 is fluidly connected within fuel and actuation system 10 with check valve 50, pressure relief valve 52, filter 54A and filter 54B.
  • Filters 54A and 54B remove contaminants from the fuel before and after being routed to and from motive pump 14, respectively, to avoid formation of blockage in passages within actuators 18A and 18B or ejector 36.
  • filter 54A comprises a screen with a bypass valve
  • filter 54B comprises a wash filter.
  • Pressure relief valve 52 allows fuel from the high pressure side of motive pump 14 to be returned to the low pressure side of motive pump 14, such as at the inlet of filter 54A. Pressure relief valve 52 typically automatically opens when pressure at the high pressure side of motive pump 14 becomes higher than a system maximum to prevent system over-pressurization.
  • Check valve 50 ensures that fuel from motive pump 14 remains above a baseline pressure in the fuel lines. In particular, fuel flow from motive pump 14 is divided between the needs of ejector 36 and actuators 18A and 18B. Ejector 36 is operable over a wide range of system pressures and need not continuously operate. Actuators 18A and 18B, however, require a minimum fuel pressure to be operable and need to operate over the entire operating envelope of gas turbine engine 19. Check valve 50 ensures that flow from motive pump 14 to actuators 18A and 18B is at a minimum pressure to ensure functionality of actuators 18A and 18B. Specifically, check valve 50 establishes a restriction before ejector 36 that maintains a back pressure between motive pump 14 and actuators 18A and 18B. In one embodiment, check valve 50 comprises a minimum pressure valve, as is known in the art. In another embodiment, check valve 50 may comprise a computer controlled valve to modulate the minimum pressure for additional optimization of both pressure and temperature.
  • main fuel pump 12 is sized to provide only the fuel flow required by distribution system 16.
  • actuators within a gas turbine engine can consume 20% - 30% of the output of the main fuel pump.
  • main fuel pump 12 need not be sized to provide additional fuel flows to actuators 18A and 18B.
  • motive pump 14 need not be increased in capacity to accommodate actuator transients because short reductions in motive flow are acceptable.
  • main fuel pump 12 can be 20% - 30% smaller and lighter.
  • Main fuel pump 12 also does not consume excessive system horsepower, such as by consuming shaft power of gas turbine engine 19, or generate excess system heat, such as by pumping unnecessary volume of fuel through pressure regulating valve 42.
  • actuators 18A and 18B can be de-coupling fuel flow to actuators 18A and 18B from main fuel pump 12, actuators 18A and 18B and all fuel lines servicing actuators 18A and 18B, can be sized for lower pressures and lower cycle fatigue. Thus, actuators 18A and 18B and their respective fuel lines can be lighter and less expensive. Additionally, by having actuators 18A and 18B powered by motive pump 14, transient disturbance from the actuators of pressure regulating valve 42 is eliminated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
EP14158333.6A 2013-03-27 2014-03-07 Système d'actionnement et de carburant pour moteur de turbine à gaz et procédé correspondant Active EP2784270B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/851,580 US9091212B2 (en) 2013-03-27 2013-03-27 Fuel and actuation system for gas turbine engine

Publications (3)

Publication Number Publication Date
EP2784270A2 true EP2784270A2 (fr) 2014-10-01
EP2784270A3 EP2784270A3 (fr) 2015-04-29
EP2784270B1 EP2784270B1 (fr) 2019-06-12

Family

ID=50238224

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14158333.6A Active EP2784270B1 (fr) 2013-03-27 2014-03-07 Système d'actionnement et de carburant pour moteur de turbine à gaz et procédé correspondant

Country Status (2)

Country Link
US (1) US9091212B2 (fr)
EP (1) EP2784270B1 (fr)

Families Citing this family (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10443503B2 (en) * 2015-03-27 2019-10-15 Pratt & Whitney Canada Corp. Fuel system for a gas turbine engine
US10119095B2 (en) * 2016-02-11 2018-11-06 T2 Energy, Llc System and method for processing algae-based products using recovered flue gas heat
US10544717B2 (en) 2016-09-07 2020-01-28 Pratt & Whitney Canada Corp. Shared oil system arrangement for an engine component and a generator
US11624326B2 (en) 2017-05-21 2023-04-11 Bj Energy Solutions, Llc Methods and systems for supplying fuel to gas turbine engines
US11267580B2 (en) * 2018-12-19 2022-03-08 Hamilton Sundstrand Corporation Fuel systems for aircraft and methods of pressurizing fuel
US20210079848A1 (en) 2019-03-20 2021-03-18 United Technologies Corporation Secondary fuel flow demand fuel pumping system
US11560845B2 (en) 2019-05-15 2023-01-24 Bj Energy Solutions, Llc Mobile gas turbine inlet air conditioning system and associated methods
US11603802B2 (en) * 2019-08-27 2023-03-14 Pratt & Whitney Canada Corp. Methods and systems for starting a gas turbine engine
US11015536B2 (en) 2019-09-13 2021-05-25 Bj Energy Solutions, Llc Methods and systems for supplying fuel to gas turbine engines
US10895202B1 (en) 2019-09-13 2021-01-19 Bj Energy Solutions, Llc Direct drive unit removal system and associated methods
US11015594B2 (en) 2019-09-13 2021-05-25 Bj Energy Solutions, Llc Systems and method for use of single mass flywheel alongside torsional vibration damper assembly for single acting reciprocating pump
US10961914B1 (en) 2019-09-13 2021-03-30 BJ Energy Solutions, LLC Houston Turbine engine exhaust duct system and methods for noise dampening and attenuation
US10815764B1 (en) 2019-09-13 2020-10-27 Bj Energy Solutions, Llc Methods and systems for operating a fleet of pumps
US11002189B2 (en) 2019-09-13 2021-05-11 Bj Energy Solutions, Llc Mobile gas turbine inlet air conditioning system and associated methods
CA3191280A1 (fr) 2019-09-13 2021-03-13 Bj Energy Solutions, Llc Methodes et systemes d`alimentation de turbines a gaz en carburant
US11555756B2 (en) 2019-09-13 2023-01-17 Bj Energy Solutions, Llc Fuel, communications, and power connection systems and related methods
CA3092865C (fr) 2019-09-13 2023-07-04 Bj Energy Solutions, Llc Sources d`alimentation et reseaux de transmission pour du materiel auxiliaire a bord d`unites de fracturation hydraulique et methodes connexes
US12065968B2 (en) 2019-09-13 2024-08-20 BJ Energy Solutions, Inc. Systems and methods for hydraulic fracturing
US10989180B2 (en) 2019-09-13 2021-04-27 Bj Energy Solutions, Llc Power sources and transmission networks for auxiliary equipment onboard hydraulic fracturing units and associated methods
CA3197583A1 (en) 2019-09-13 2021-03-13 Bj Energy Solutions, Llc Fuel, communications, and power connection systems and related methods
US11708829B2 (en) 2020-05-12 2023-07-25 Bj Energy Solutions, Llc Cover for fluid systems and related methods
US10968837B1 (en) 2020-05-14 2021-04-06 Bj Energy Solutions, Llc Systems and methods utilizing turbine compressor discharge for hydrostatic manifold purge
US11428165B2 (en) 2020-05-15 2022-08-30 Bj Energy Solutions, Llc Onboard heater of auxiliary systems using exhaust gases and associated methods
US11208880B2 (en) 2020-05-28 2021-12-28 Bj Energy Solutions, Llc Bi-fuel reciprocating engine to power direct drive turbine fracturing pumps onboard auxiliary systems and related methods
US11208953B1 (en) 2020-06-05 2021-12-28 Bj Energy Solutions, Llc Systems and methods to enhance intake air flow to a gas turbine engine of a hydraulic fracturing unit
US10961908B1 (en) 2020-06-05 2021-03-30 Bj Energy Solutions, Llc Systems and methods to enhance intake air flow to a gas turbine engine of a hydraulic fracturing unit
US11109508B1 (en) 2020-06-05 2021-08-31 Bj Energy Solutions, Llc Enclosure assembly for enhanced cooling of direct drive unit and related methods
US11066915B1 (en) 2020-06-09 2021-07-20 Bj Energy Solutions, Llc Methods for detection and mitigation of well screen out
US11111768B1 (en) 2020-06-09 2021-09-07 Bj Energy Solutions, Llc Drive equipment and methods for mobile fracturing transportation platforms
US11022526B1 (en) 2020-06-09 2021-06-01 Bj Energy Solutions, Llc Systems and methods for monitoring a condition of a fracturing component section of a hydraulic fracturing unit
US10954770B1 (en) 2020-06-09 2021-03-23 Bj Energy Solutions, Llc Systems and methods for exchanging fracturing components of a hydraulic fracturing unit
US11028677B1 (en) 2020-06-22 2021-06-08 Bj Energy Solutions, Llc Stage profiles for operations of hydraulic systems and associated methods
US11939853B2 (en) 2020-06-22 2024-03-26 Bj Energy Solutions, Llc Systems and methods providing a configurable staged rate increase function to operate hydraulic fracturing units
US11933153B2 (en) 2020-06-22 2024-03-19 Bj Energy Solutions, Llc Systems and methods to operate hydraulic fracturing units using automatic flow rate and/or pressure control
US11125066B1 (en) 2020-06-22 2021-09-21 Bj Energy Solutions, Llc Systems and methods to operate a dual-shaft gas turbine engine for hydraulic fracturing
US11473413B2 (en) 2020-06-23 2022-10-18 Bj Energy Solutions, Llc Systems and methods to autonomously operate hydraulic fracturing units
US11466680B2 (en) 2020-06-23 2022-10-11 Bj Energy Solutions, Llc Systems and methods of utilization of a hydraulic fracturing unit profile to operate hydraulic fracturing units
US11149533B1 (en) 2020-06-24 2021-10-19 Bj Energy Solutions, Llc Systems to monitor, detect, and/or intervene relative to cavitation and pulsation events during a hydraulic fracturing operation
US11220895B1 (en) 2020-06-24 2022-01-11 Bj Energy Solutions, Llc Automated diagnostics of electronic instrumentation in a system for fracturing a well and associated methods
US11193361B1 (en) 2020-07-17 2021-12-07 Bj Energy Solutions, Llc Methods, systems, and devices to enhance fracturing fluid delivery to subsurface formations during high-pressure fracturing operations
US11639654B2 (en) 2021-05-24 2023-05-02 Bj Energy Solutions, Llc Hydraulic fracturing pumps to enhance flow of fracturing fluid into wellheads and related methods
US20230193864A1 (en) * 2021-12-17 2023-06-22 Hamilton Sundstrand Corporation Distributed network of heat exchangers

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4069662A (en) 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
US4487016A (en) 1980-10-01 1984-12-11 United Technologies Corporation Modulated clearance control for an axial flow rotary machine

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3275061A (en) * 1964-01-02 1966-09-27 Boeing Co Fuel feeding systems
US3279522A (en) * 1964-01-02 1966-10-18 Boeing Co Fuel feeding systems
US4304093A (en) 1979-08-31 1981-12-08 General Electric Company Variable clearance control for a gas turbine engine
US4338061A (en) 1980-06-26 1982-07-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Control means for a gas turbine engine
US5116362A (en) * 1990-12-03 1992-05-26 United Technologies Corporation Fuel metering and actuation system
US6487847B1 (en) 2000-11-03 2002-12-03 General Electric Company Gas turbine engine fuel control system
US6651441B2 (en) 2002-01-22 2003-11-25 Hamilton Sundstrand Fluid flow system for a gas turbine engine
US6810674B2 (en) * 2002-07-18 2004-11-02 Argo-Tech Corporation Fuel delivery system
US7185485B2 (en) 2003-05-29 2007-03-06 Honeywell International Inc. Method and system for failure accommodation of gas generator fuel metering system
US7007452B1 (en) * 2003-06-13 2006-03-07 Woodward Governor Company Fuel system for a gas turbine engine
US7216487B2 (en) * 2004-09-16 2007-05-15 Hamilton Sundstrand Metering demand fuel system for gas turbine engines
US20060150631A1 (en) * 2005-01-11 2006-07-13 General Electric Company Liquid fuel recirculation system and method
JP4119908B2 (ja) 2005-09-14 2008-07-16 三菱重工業株式会社 ガスタービンの燃焼制御装置
US7966995B2 (en) 2007-09-05 2011-06-28 Honeywell International Inc. Dual level pressurization control based on fuel flow to one or more gas turbine engine secondary fuel loads
FR2922264B1 (fr) 2007-10-12 2009-12-04 Hispano Suiza Sa Circuit d'alimentation en carburant d'un moteur d'aeronef
US8256222B2 (en) * 2008-02-11 2012-09-04 Honeywell International Inc. Direct metering fuel control with integral electrical metering pump and actuator servo pump
US8127548B2 (en) * 2008-02-21 2012-03-06 Honeywell International Inc. Hybrid electrical/mechanical turbine engine fuel supply system
US8776529B2 (en) 2010-09-27 2014-07-15 Hamilton Sundstrand Corporation Critical flow nozzle for controlling fuel distribution and burner stability
US8893466B2 (en) 2011-03-18 2014-11-25 Hamilton Sundstrand Corporation Dual pump fuel flow system for a gas turbine engine and method of controlling
US8666632B2 (en) 2011-04-20 2014-03-04 Hamilton Sundstrand Corporation Distributed aircraft engine fuel system

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4069662A (en) 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
US4487016A (en) 1980-10-01 1984-12-11 United Technologies Corporation Modulated clearance control for an axial flow rotary machine

Also Published As

Publication number Publication date
EP2784270A3 (fr) 2015-04-29
EP2784270B1 (fr) 2019-06-12
US9091212B2 (en) 2015-07-28
US20140290266A1 (en) 2014-10-02

Similar Documents

Publication Publication Date Title
EP2784270B1 (fr) Système d'actionnement et de carburant pour moteur de turbine à gaz et procédé correspondant
EP3232036B1 (fr) Système de carburant à double pompe avec connexion de partage de pompe
US8302406B2 (en) Fuel delivery and control system including a positive displacement actuation pump with a variable pressure regulator supplementing a fixed displacement main fuel pump
US8166765B2 (en) Fuel delivery and control system including a variable displacement actuation pump supplementing a fixed displacement main pump
US8196385B2 (en) Turbomachine control system
EP2891781B1 (fr) Systeme de regulation de carburant d'un moteur
RU2674301C2 (ru) Подающий текучую среду контур с устройствами изменяемой геометрии и без объемного насоса для турбомашины
US9151180B2 (en) Lubrication driven gas turbine engine actuation system
EP2796688B1 (fr) Système permettant de commander deux pompes à déplacement positif
US11203978B2 (en) Dual pump unit with boost pump
US20220178544A1 (en) Method of operating an aircraft engine and fuel system using multiple fuel types
US20220178306A1 (en) Method of operating an aircraft engine and fuel system using multiple fuel types
EP3022425B1 (fr) Recirculation d'écoulement asservie pour système de combustible de moteur d'avion à rendement thermique perfectionné
US11719128B2 (en) Lubrication system with anti-priming feature

Legal Events

Date Code Title Description
17P Request for examination filed

Effective date: 20140307

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F02C 7/236 20060101ALI20150324BHEP

Ipc: F02C 9/26 20060101ALI20150324BHEP

Ipc: F01D 17/10 20060101AFI20150324BHEP

R17P Request for examination filed (corrected)

Effective date: 20151029

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20170403

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20181218

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1142802

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190615

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602014048061

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190612

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190912

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190912

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190913

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1142802

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191014

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191012

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602014048061

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

26N No opposition filed

Effective date: 20200313

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200224

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

PG2D Information on lapse in contracting state deleted

Ref country code: IS

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602014048061

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200307

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201001

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200307

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190612

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230522

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240220

Year of fee payment: 11

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240220

Year of fee payment: 11